Thrust-terminating system conceived to reduce thrust of solid-propellant rocket motor in controlled manner such that thrust loads not increased or decreased beyond predictable levels. Concept involves explosively cutting opposing venting pairs in case of rocket motor above nozzles to initiate venting of chamber and reduction of thrust. Vents sized and numbered to control amount and rate of reduction in thrust.
Reducing Thrusts In Solid-Fuel Rockets
NASA Tech Briefs ; 13 , 4
1989-04-01
Miscellaneous
No indication
English
Optimum Thrusts for Rockets in Vertical Flight in Vacuum
NTIS | 1960
|NTIS | 1967
|NTIS | 1973
|Acoustic instability in solid fuel rockets
Engineering Index Backfile | 1960
|Engineering Index Backfile | 1965
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